Blade for a turbo machine, blade assembly, gas turbine, and method for manufacturing a blade for a turbo machine

Abstract

A blade for turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction between a root end and a tip end and including an inner void extending from the root end in the radial direction, a root body integrally formed with the airfoil body, extending from the root end of the air foil body to a bottom end in the radial direction, and including a receiving slot extending from the bottom end in the radial direction and opening into the inner void of the air foil body, and an insert positioned in the receiving slot of the root body and including a plurality of through holes extending in the radial direction to form a fluid connection to the inner void of the air foil body.

What is claimed is: 
     
       1. A blade for a turbo machine comprising:
 an airfoil body extending in a radial direction between a root end and a tip end and including an inner void extending from the root end in the radial direction; 
 a root body integrally formed with the airfoil body, extending from the root end of the air foil body to a bottom end in the radial direction, and including a receiving slot extending from the bottom end in the radial direction and opening into the inner void of the air foil body; and 
 an insert positioned in the receiving slot of the root body and including a plurality of through holes extending in the radial direction to form a fluid connection to the inner void of the air foil body. 
 
     
     
       2. The blade according to  claim 1 , wherein the root body extends between a front end and an aft end along an axial direction running across the radial direction,
 wherein the receiving slot extends fully between the front end and the aft end of the root body, and the insert positioned in the receiving slot extends between the front end and the aft end of the root body. 
 
     
     
       3. The blade according to  claim 2 , wherein the insert comprises a first end plate formed at a first axial end of the insert and a second end plate formed at a second axial end of the insert,
 wherein the first end plate abuts a first end surface forming the front end of the root body, and the second end plate abuts a second end surface forming the aft end of the root body. 
 
     
     
       4. The blade according to  claim 2 , wherein the through holes are formed in a central region of the insert that overlaps with the inner void of the airfoil body with respect to the axial direction. 
     
     
       5. The blade according to  claim 1 , wherein the root body extends between a front end and an aft end along an axial direction running across the radial direction,
 wherein the receiving slot extends in the axial direction and ends apart from the front end and the aft end. 
 
     
     
       6. The blade according to  claim 1 , wherein the insert is brazed to the root body or friction fit into the receiving slot. 
     
     
       7. The blade according to  claim 1 , wherein the plurality of through holes of the insert have a circular, an elliptic, or racetrack shaped cross-section,
 wherein the plurality of through holes of the insert are arranged in a row along an insert axial direction, and 
 wherein a ratio between a distance between adjacent through holes in the insert axial direction and a diameter of the through holes with respect to the insert axial direction is greater than 1. 
 
     
     
       8. The blade according to  claim 1 , wherein the insert has a thickness with respect to an insert thickness direction, and
 wherein a ratio between a diameter and the thickness of the through holes with respect to the insert thickness direction is in a range of 0.1 to 0.8. 
 
     
     
       9. The blade according to  claim 1 , wherein the insert further includes grooves formed in a circumferential surface of the insert and extending in the radial direction between opposite radial ends of the insert, and the grooves together with an inner surface of the receiving slot form fluid channels connected to the inner void of the airfoil body. 
     
     
       10. A blade assembly comprising:
 a plurality of blades; and 
 a rotor disk to which the plurality of blades are coupled, 
 wherein each of the plurality of blades comprises: 
 an airfoil body extending in a radial direction between a root end and a tip end and including an inner void extending from the root end in the radial direction; 
 a root body integrally formed with the airfoil body, extending from the root end of the air foil body to a bottom end in the radial direction, and including a receiving slot extending from the bottom end in the radial direction and opening into the inner void of the air foil body; and 
 an insert positioned in the receiving slot of the root body and including a plurality of through holes extending in the radial direction to form a fluid connection to the inner void of the air foil body. 
 
     
     
       11. The blade assembly according to  claim 10 , wherein the root body extends between a front end and an aft end along an axial direction running across the radial direction,
 wherein the receiving slot extends fully between the front end and the aft end of the root body, and the insert positioned in the receiving slot extends between the front end and the aft end of the root body, and 
 wherein the insert comprises a first end plate formed at a first axial end of the insert and a second end plate formed at a second axial end of the insert, and the first end plate abuts a first end surface forming the front end of the root body, and the second end plate abuts a second end surface forming the aft end of the root body. 
 
     
     
       12. The blade assembly according to  claim 11 , wherein the through holes are formed in a central region of the insert that overlaps with the inner void of the airfoil body with respect to the axial direction, and
 wherein the root body extends between a front end and an aft end along an axial direction running across the radial direction, and the receiving slot extends in the axial direction and ends apart from the front end and the aft end. 
 
     
     
       13. The blade assembly according to  claim 10 , wherein the insert is brazed to the root body or friction fit into the receiving slot,
 wherein the through holes of the insert have a circular, an elliptic, or racetrack shaped cross-section, and the through holes of the insert are arranged in a row along an insert axial direction, and 
 wherein a ratio between a distance between adjacent through holes in the insert axial direction and a diameter of the through holes with respect to the insert axial direction is greater than 1. 
 
     
     
       14. The blade assembly according to  claim 10 , wherein the insert has a thickness with respect to an insert thickness direction, and
 wherein a ratio between a diameter and the thickness of the through holes with respect to the insert thickness direction is in a range of 0.1 to 0.8. 
 
     
     
       15. The blade assembly according to  claim 9 , wherein the insert further includes grooves formed in a circumferential surface of the insert and extending in the radial direction between opposite radial ends of the insert, and the grooves together with an inner surface of the receiving slot form fluid channels connected to the inner void of the airfoil body. 
     
     
       16. A gas turbine comprising:
 a blade assembly comprising a plurality of blades and a rotor disk to which the plurality of blades are coupled, 
 wherein each of the plurality of blades comprises: 
 an airfoil body extending in a radial direction between a root end and a tip end and including an inner void extending from the root end in the radial direction; 
 a root body integrally formed with the airfoil body, extending from the root end of the air foil body to a bottom end in the radial direction, and including a receiving slot extending from the bottom end in the radial direction and opening into the inner void of the air foil body; and 
 an insert positioned in the receiving slot of the root body and including a plurality of through holes extending in the radial direction to form a fluid connection to the inner void of the air foil body. 
 
     
     
       17. The gas turbine according to  claim 16 , wherein the root body extends between a front end and an aft end along an axial direction running across the radial direction,
 wherein the receiving slot extends fully between the front end and the aft end of the root body, and the insert positioned in the receiving slot extends between the front end and the aft end of the root body, and 
 wherein the insert comprises a first end plate formed at a first axial end of the insert and a second end plate formed at a second axial end of the insert, and the first end plate abuts a first end surface forming the front end of the root body, and the second end plate abuts a second end surface forming the aft end of the root body. 
 
     
     
       18. The gas turbine according to  claim 17 , wherein the through holes are formed in a central region of the insert that overlaps with the inner void of the airfoil body with respect to the axial direction, and
 wherein the root body extends between a front end and an aft end along an axial direction running across the radial direction, and the receiving slot extends in the axial direction and ends apart from the front end and the aft end. 
 
     
     
       19. The gas turbine according to  claim 16 , wherein the insert is brazed to the root body or friction fit into the receiving slot,
 wherein the through holes of the insert have a circular, an elliptic, or racetrack shaped cross-section, and the through holes of the insert are arranged in a row along an insert axial direction, and 
 wherein a ratio between a distance between adjacent through holes in the insert axial direction and a diameter of the through holes with respect to the insert axial direction is greater than 1. 
 
     
     
       20. The gas turbine according to  claim 16 , wherein the insert has a thickness with respect to an insert thickness direction,
 wherein a ratio between a diameter and the thickness of the through holes with respect to the insert thickness direction is in a range of 0.1 to 0.8, and 
 wherein the insert further includes grooves formed in a circumferential surface of the insert and extending in the radial direction between opposite radial ends of the insert, and the grooves together with an inner surface of the receiving slot form fluid channels connected to the inner void of the airfoil body.